Automated cooling design methodology for combustor walls

An automated cooling design procedure for aircraft engine combustors has been developed which uses a converged CFD flow solution and produces a detailed temperature distribution in the liners, dome, etc. of a combustor. The output of the automated procedure is the following: a detailed wall temperature and heat flux distribution; arrangement of effusion cooling holes, starter slots, and impingement cooling holes; the cooling flow splits in various zones which produce acceptable wall temperatures for the most severe cycle conditions imposed on the engine.